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Non-steady burning effect on solid rocket motor performance

Tahsini, A. M ; Sharif University of Technology | 2007

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  1. Type of Document: Article
  2. DOI: 10.2514/6.2007-777
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2007
  4. Abstract:
  5. Solid rocket performance during rapid pressure excursions differs greatly from predictions based on steady state burning rate data. Rapid pressurization following a chamber filling interval produces indicated burning rate overshoots. Transient internal ballistics of a solid propellant rocket motor during rapid pressurization part of chamber filling phase has been considered in this work. Quasi one-dimensional unsteady Euler equations with a transient propellant burning model that accounts for the effects of time rate of change of the chamber pressure on the burning rate have been used to simulate the internal ballistics of rocket motors. The compressible convective flow solver used in this study is based on Roe's scheme. The effects of rapid chamber pressure change on the propellant and motor transient behavior have been studied. Furthermore, prediction of the level of pressurization rate has been achieved
  6. Keywords:
  7. Combustion ; Compressible flow ; Euler equations ; Pressure effects ; Pressurization ; Solid propellants ; Chamber filling ; Overshoots ; Pressure excursions ; Transient internal ballistics ; Rocket engines
  8. Source: 45th AIAA Aerospace Sciences Meeting 2007, Reno, NV, 8 January 2007 through 11 January 2007 ; Volume 14 , 2007 , Pages 9531-9536 ; 1563478900 (ISBN); 9781563478901 (ISBN)
  9. URL: https://arc.aiaa.org/doi/abs/10.2514/6.2007-777